S3016-095-87 (s3016-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3016-095-87 (s3016-il) Reynolds number: 100,000 Max Cl/Cd: 48.46 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3016-il-100000-n5.txt Download as CSV file: xf-s3016-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3016-095-87
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4018 0.11992 0.11528 -0.0094 1.0000 0.0320
-11.000 -0.3940 0.11630 0.11166 -0.0094 1.0000 0.0303
-10.750 -0.4880 0.11867 0.11364 -0.0059 1.0000 0.0308
-10.500 -0.4831 0.11473 0.10972 -0.0071 1.0000 0.0292
-10.250 -0.4810 0.11024 0.10527 -0.0090 1.0000 0.0277
-9.750 -0.4905 0.09681 0.09195 -0.0174 1.0000 0.0236
-9.500 -0.4896 0.09255 0.08774 -0.0191 1.0000 0.0234
-9.250 -0.4898 0.08808 0.08331 -0.0213 1.0000 0.0231
-9.000 -0.4920 0.08316 0.07845 -0.0240 1.0000 0.0229
-8.750 -0.4951 0.07815 0.07351 -0.0271 1.0000 0.0227
-8.500 -0.5009 0.07256 0.06799 -0.0313 1.0000 0.0225
-8.250 -0.5104 0.06610 0.06156 -0.0369 1.0000 0.0221
-8.000 -0.5186 0.05991 0.05528 -0.0406 1.0000 0.0219
-7.750 -0.5248 0.05438 0.04957 -0.0428 1.0000 0.0217
-7.500 -0.5279 0.04937 0.04430 -0.0436 1.0000 0.0217
-7.250 -0.5289 0.04473 0.03928 -0.0433 1.0000 0.0222
-7.000 -0.5274 0.04098 0.03510 -0.0418 1.0000 0.0228
-6.750 -0.5243 0.03803 0.03168 -0.0394 1.0000 0.0234
-6.500 -0.5209 0.03507 0.02835 -0.0369 1.0000 0.0241
-6.250 -0.5142 0.03257 0.02556 -0.0345 1.0000 0.0246
-6.000 -0.4991 0.03018 0.02283 -0.0332 0.9980 0.0253
-5.750 -0.4688 0.02769 0.01991 -0.0346 0.9914 0.0263
-5.500 -0.4368 0.02563 0.01749 -0.0359 0.9852 0.0281
-5.250 -0.4039 0.02414 0.01564 -0.0371 0.9793 0.0315
-5.000 -0.3713 0.02233 0.01357 -0.0381 0.9735 0.0336
-4.750 -0.3378 0.02086 0.01203 -0.0396 0.9686 0.0361
-4.500 -0.3058 0.01996 0.01101 -0.0406 0.9619 0.0411
-4.250 -0.2714 0.01891 0.00980 -0.0420 0.9568 0.0454
-4.000 -0.2422 0.01808 0.00890 -0.0424 0.9490 0.0506
-3.750 -0.2089 0.01725 0.00801 -0.0435 0.9432 0.0610
-3.500 -0.1813 0.01642 0.00736 -0.0437 0.9349 0.0981
-3.250 -0.1500 0.01562 0.00687 -0.0446 0.9288 0.1802
-3.000 -0.1246 0.01498 0.00664 -0.0445 0.9199 0.2768
-2.750 -0.0970 0.01428 0.00649 -0.0446 0.9130 0.4055
-2.500 -0.0720 0.01381 0.00636 -0.0439 0.9041 0.5060
-2.250 -0.0453 0.01342 0.00624 -0.0432 0.8963 0.6005
-2.000 -0.0184 0.01310 0.00614 -0.0422 0.8884 0.6917
-1.750 0.0106 0.01286 0.00608 -0.0415 0.8803 0.7809
-1.500 0.0540 0.01270 0.00597 -0.0435 0.8743 0.8652
-1.250 0.1044 0.01262 0.00578 -0.0474 0.8677 0.9236
-1.000 0.1531 0.01255 0.00556 -0.0512 0.8603 0.9616
-0.750 0.1992 0.01248 0.00534 -0.0547 0.8513 0.9914
-0.500 0.2306 0.01244 0.00516 -0.0555 0.8410 1.0000
-0.250 0.2527 0.01244 0.00504 -0.0541 0.8295 1.0000
0.000 0.2745 0.01246 0.00496 -0.0528 0.8166 1.0000
0.250 0.2966 0.01249 0.00489 -0.0515 0.8034 1.0000
0.500 0.3190 0.01251 0.00481 -0.0502 0.7897 1.0000
0.750 0.3416 0.01252 0.00475 -0.0489 0.7754 1.0000
1.000 0.3646 0.01255 0.00469 -0.0476 0.7607 1.0000
1.250 0.3878 0.01258 0.00465 -0.0464 0.7458 1.0000
1.500 0.4112 0.01261 0.00461 -0.0453 0.7305 1.0000
1.750 0.4348 0.01267 0.00461 -0.0442 0.7140 1.0000
2.000 0.4586 0.01273 0.00464 -0.0431 0.6963 1.0000
2.250 0.4825 0.01280 0.00465 -0.0421 0.6782 1.0000
2.500 0.5066 0.01287 0.00465 -0.0410 0.6596 1.0000
2.750 0.5306 0.01298 0.00471 -0.0400 0.6386 1.0000
3.000 0.5547 0.01311 0.00478 -0.0390 0.6175 1.0000
3.250 0.5788 0.01327 0.00488 -0.0380 0.5939 1.0000
3.500 0.6027 0.01345 0.00499 -0.0370 0.5694 1.0000
3.750 0.6265 0.01367 0.00516 -0.0361 0.5436 1.0000
4.000 0.6502 0.01393 0.00533 -0.0351 0.5163 1.0000
4.250 0.6736 0.01423 0.00554 -0.0342 0.4878 1.0000
4.500 0.6968 0.01456 0.00578 -0.0333 0.4586 1.0000
4.750 0.7198 0.01494 0.00607 -0.0324 0.4293 1.0000
5.000 0.7426 0.01535 0.00642 -0.0315 0.4005 1.0000
5.250 0.7652 0.01579 0.00679 -0.0306 0.3728 1.0000
5.500 0.7876 0.01627 0.00719 -0.0297 0.3470 1.0000
5.750 0.8099 0.01678 0.00763 -0.0288 0.3222 1.0000
6.000 0.8321 0.01729 0.00811 -0.0280 0.2997 1.0000
6.250 0.8539 0.01786 0.00867 -0.0271 0.2788 1.0000
6.500 0.8759 0.01842 0.00922 -0.0263 0.2592 1.0000
6.750 0.8975 0.01900 0.00981 -0.0254 0.2405 1.0000
7.000 0.9187 0.01963 0.01043 -0.0246 0.2234 1.0000
7.250 0.9395 0.02027 0.01108 -0.0236 0.2072 1.0000
7.500 0.9604 0.02092 0.01182 -0.0227 0.1914 1.0000
7.750 0.9808 0.02160 0.01256 -0.0218 0.1765 1.0000
8.000 1.0007 0.02233 0.01334 -0.0208 0.1626 1.0000
8.250 1.0200 0.02309 0.01416 -0.0198 0.1491 1.0000
8.500 1.0385 0.02391 0.01503 -0.0187 0.1364 1.0000
8.750 1.0560 0.02480 0.01596 -0.0175 0.1249 1.0000
9.000 1.0732 0.02570 0.01695 -0.0163 0.1133 1.0000
9.250 1.0899 0.02664 0.01806 -0.0150 0.1023 1.0000
9.500 1.1052 0.02767 0.01920 -0.0136 0.0918 1.0000
9.750 1.1187 0.02879 0.02039 -0.0121 0.0823 1.0000
10.000 1.1299 0.02999 0.02163 -0.0105 0.0733 1.0000
10.250 1.1408 0.03119 0.02298 -0.0088 0.0639 1.0000
10.500 1.1487 0.03246 0.02436 -0.0069 0.0545 1.0000
10.750 1.1537 0.03391 0.02588 -0.0048 0.0458 1.0000
11.000 1.1549 0.03570 0.02765 -0.0029 0.0396 1.0000
11.250 1.1583 0.03753 0.02970 -0.0012 0.0339 1.0000
11.500 1.1540 0.04000 0.03225 0.0004 0.0303 1.0000
11.750 1.1531 0.04244 0.03490 0.0017 0.0272 1.0000
12.000 1.1502 0.04514 0.03775 0.0024 0.0243 1.0000
12.250 1.1447 0.04821 0.04094 0.0027 0.0227 1.0000
12.500 1.1357 0.05193 0.04475 0.0025 0.0215 1.0000
12.750 1.1307 0.05549 0.04855 0.0021 0.0205 1.0000
13.000 1.1234 0.05955 0.05282 0.0012 0.0194 1.0000
13.250 1.1140 0.06415 0.05762 -0.0004 0.0184 1.0000
13.500 1.1041 0.06907 0.06271 -0.0023 0.0180 1.0000
13.750 1.0931 0.07444 0.06826 -0.0047 0.0177 1.0000
14.000 1.0810 0.08027 0.07427 -0.0075 0.0174 1.0000
14.250 1.0675 0.08667 0.08083 -0.0108 0.0171 1.0000
14.500 1.0542 0.09337 0.08769 -0.0144 0.0170 1.0000
14.750 1.0398 0.10058 0.09507 -0.0183 0.0170 1.0000
15.000 1.0248 0.10824 0.10289 -0.0224 0.0171 1.0000
15.250 1.0082 0.11662 0.11143 -0.0271 0.0172 1.0000
15.500 0.9896 0.12585 0.12083 -0.0321 0.0174 1.0000
15.750 0.9666 0.13687 0.13201 -0.0382 0.0178 1.0000
16.000 0.9349 0.15138 0.14659 -0.0459 0.0186 1.0000
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Polar data table (+)
Polar graphs
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